火箭发动机
- 名rocket engine;rocket motor
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固体火箭发动机工业CT探测系统
Industrial CT inspecting system for solid rocket motor
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固体火箭发动机燃烧室X射线探伤中像质计的应用
Application of Image Quality Indicator in X-Radiographic Examination of Solid Rocket Motor Chamber
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用串行和并行SIMPLE算法对液体火箭发动机燃烧室内的复杂流动进行了数值模拟。
The complex flow was simulated with sequential and parallel SIMPLE algorithm in the combustion chamber of liquid rocket engine .
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固体火箭发动机集成初步设计CAD系统研究
Some Progress in Development of Chinese Integrated Preliminary CAD Design of Solid Rocket Motors
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认识到建立固体火箭发动机燃烧室X射线探伤像质计标准势在必行。
It was considered that the establishment of radiographic IQI standard for solid rocket motor chamber was necessary .
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介绍一种应用CAT技术确定固体火箭发动机燃烧时间的新方法。
The paper introduces a new method of measuring combustion time with CAT technique for solid rocket engine .
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火箭发动机可靠性增长评估的Bayes方法
The Bayes Method for Rocket Engine Reliability Growth Evaluation
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基于爆破试验的CFRP固体火箭发动机壳体的可靠性设计
Reliability design of CFRP solid rocket motor vessel based on the burst experiment
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H2O2-PE固液火箭发动机低频不稳定燃烧研究
Research on low frequency unstable combustion of H_2O_2-PE hybrid rocket motors
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H2O2-PE固液混合火箭发动机试验研究
Experimental study on hydrogen peroxide and polyethylene hybrid rocket motors
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Elman型神经网络在液体火箭发动机故障预测中的应用
Application of Elman Neural Network on Liquid Rocket Engine Fault Prediction
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用激光瞬态F-P干涉仪对火箭发动机真实燃气射流进行高速摄影
To Take the High-Speed Photography for Real Exhaust Plumes of Rocket Engine with Laser Transient F-P Interferometer
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85%H2O2-PE固液火箭发动机工作过程研究
Research on Working Process of the 85 % H_2O_2-PE Hybrid Rocket Motor
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Weibull寿命模型下火箭发动机可靠性增长试验的LS-Bayes分析
The LS-Bayes Analysis for Rocket Engine Reliability Growth Test under Weibull Life Model
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在此基础上,将MDF方法应用于固体火箭发动机内弹道计算,通过算例验证了MDF方法的适用性。
Basing research above , the MDF method has been used for SRM internal ballistics calculation , which has been test by two cases .
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以平台液体火箭发动机为研究对象,改进和完善了用于发动机实时故障检测的自适应阈值门限算法(ATA算法),提高了算法检测的适用性。
The ATA algorithm was improved for the platform for liquid-propellant rocket engines and the applicability of the algorithm was improved .
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讨论光纤布拉格光栅(FBG)传感技术用于固体火箭发动机结构应变场、温度场和损伤状况健康监测的可行性。
The feasibility of applying fiber gratings sensing on health monitoring of solid rocket motor ( SRM ) is discussed , including the strain measurement , temperature measurement and damage measurement .
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试验结果表明,与使用EPDM绝热层材料相比,使用RTV绝热层材料,火箭发动机燃烧室羽流具有较高的信号透过率;
The test results show that the plume from the rocket chamber using RTV insulation material has higher signature penetrating rate than that using EPDM insulation material .
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因此,MATA适合于液体火箭发动机涡轮泵的实时故障检测。
As a conclusion , MATA is suitable for the real time fault detection of LRE turbopump .
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在大约时速200英里时他将启动为火箭发动机传送HTP的泵。
At about 200mph he will start the pump to deliver the HTP into the rocket .
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利用N2O催化分解原理,设计了一个用于启动N2O混合火箭发动机的催化点火器。固液混合火箭发动机是采用液体作为氧化剂,固体作为燃料的一种典型的混合火箭发动机。
An innovative igniter based on catalytic decomposition of N2O was designed and manufactured . In a typical hybrid , the fuel is a solid and the oxidizer is a liquid .
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用RTR技术研究固体火箭发动机燃烧室中粒子运动轨迹(I)可行性分析与试验研究
Experimental study of particles trajectory in firing solid rocket motor with RTR TECHNIQUE part ( I ) analysis of feasibility and experimental results
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本文选用SSTK-ω湍流模型对采用烧结多孔介质进行发汗冷却的液体O2/H2火箭发动机推力室进行了全场耦合数值模拟研究。
In this study , the SST k - ω turbulence model was used to simulate the coupled whole field for the transpiration cooling of a thruster in a liquid O2 / H2 propellant rocket engine .
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用Fluent计算流体力学软件对固体火箭发动机喷管流场进行了数值计算,研究了喷管收敛半角、喷管喉部上游圆弧曲率半径和喉部圆柱段长度对喷管流场的影响。
Nozzle flow field of SRM was numerically simulated with Fluent software . The effects of nozzle convergent half angle , radius of curvature on upstream of throat section and length of throat cylinder on flow field are investigated .
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基于MSPCA的液体火箭发动机试车台氢供应系统传感器故障诊断方法
Method of Sensor Fault Diagnosis in Liquid Rocket Engine Ground Testing Bed Hydrogen Providing System Based on MSPCA
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采用新型的Flash单片机、信号采集电路与温控电路等构成一个对固体火箭发动机温控系统,满足其固体火药的初始温度设计要求。
The paper states the way of incorporating a new type of flash singlechip , signal acquisition circuits , temperature-control circuits into a temperature-control system for a soild rocket motor , so as to fulfil the settings on the initial temperature of its charge .
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利用水力系数(C(ADE))的性质和现有液体火箭发动机管路系统中压力或流量的测量值,进行适当分段组合,计算出相应的压力和水力系统改变量。
Using the definition of hydraulic coefficient and existent measurements of pressure or flow in pipes of liquid rocket engine , the pressure and the change amount of hydraulic coefficient will be determined according to appropriate calculation of a certain separate pipe .
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CRTP火箭发动机测试系统
CRTP Rocket Engine Testing System
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介绍了一种以数据采集卡为底层硬件,基于VC++界面和MATLAB数据处理混合编程开发的虚拟仪器技术,并将它用于火箭发动机推进剂药柱粘弹性性能测试。
The paper presents a development method of virtual instrument technology , which uses plug-in DAQ board as hardware and the hybrid programm on the basis of VC + + interface and MATLAB data treatment . The method is used to measure the viscoelastic properties of the propellant grain .
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文中将小波分析理论、神经网络技术与D-S证据理论引入到火箭发动机故障诊断中,提出了一种适于发动机故障诊断的小波神经网络信息融合方法。
This text puts forward a kind of information fusion methods according to wavelet neural network that be suitable for fault diagnosis of rocket engine by leading into wavelet analysis theories , neural network technique and D-S evidence theory .